EP2378070A2 - Entretoise de moteur de turbine - Google Patents

Entretoise de moteur de turbine Download PDF

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Publication number
EP2378070A2
EP2378070A2 EP11162097A EP11162097A EP2378070A2 EP 2378070 A2 EP2378070 A2 EP 2378070A2 EP 11162097 A EP11162097 A EP 11162097A EP 11162097 A EP11162097 A EP 11162097A EP 2378070 A2 EP2378070 A2 EP 2378070A2
Authority
EP
European Patent Office
Prior art keywords
turbine
spacer
orifice
stage
aft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP11162097A
Other languages
German (de)
English (en)
Other versions
EP2378070A3 (fr
EP2378070B1 (fr
Inventor
Anantha Padmanabhan Bhagavetheeswaran
Rohit Pruthi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2378070A2 publication Critical patent/EP2378070A2/fr
Publication of EP2378070A3 publication Critical patent/EP2378070A3/fr
Application granted granted Critical
Publication of EP2378070B1 publication Critical patent/EP2378070B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/72—Application in combination with a steam turbine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the subject matter disclosed herein relates to a turbine engine with a spacer.
  • a turbine includes a spacer having an annular body formed with opposing outward and inward surfaces and an orifice extending through the body from the outward to the inward surface, an assembly to secure the spacer around a rotor axially between sequential buckets of a forward turbine stage and an aft turbine stage, the spacer forming an annular passage around the rotor into which a fluid flows through the orifice and a circuit fluidly coupled to the annular passage to deliver the fluid from between the sequential buckets of the forward turbine stage and the aft turbine stage to an axial location forward of the forward turbine stage.
  • a turbine engine includes a rotor disposed within a casing to define a passage through which fluid flows from a forward to an aft turbine stage at which the fluid is relatively cooled, a spacer having an annular body formed with opposing outward and inward surfaces and an orifice extending through the body from the outward to the inward surface, an assembly to secure the spacer around the rotor axially between sequential buckets of the forward and the aft stage, the spacer forming an annular passage around the rotor into which the cooled fluid flows through the orifice and a circuit fluidly coupled to the annular passage to deliver the cooled fluid from between the sequential buckets of the forward and the aft stage to an axial location forward of the forward stage.
  • a steam turbine engine includes a rotor disposed within a casing to define a passage through which steam flows from a forward to an aft turbine stage at which the steam is relatively cooled, a spacer having an annular body formed with opposing outward and inward surfaces and an orifice extending through the body from the outward to the inward surface, an assembly to secure the spacer around the rotor axially between sequential buckets of the forward and the aft stage, the spacer forming an annular passage around the rotor into which the cooled steam flows through the orifice and a circuit fluidly coupled to the annular passage to deliver the cooled steam from between the sequential buckets of the forward and the aft stage to an axial location forward of the forward stage.
  • the sole figure is a schematic side sectional view of a turbine.
  • a turbine 10 such as a steam turbine of a steam turbine engine
  • the turbine 10 includes a casing 20 and a rotor 30 rotatably disposed within the casing 20 to define a fluid path 40 extending at least from a forward turbine stage 50 to an aft turbine stage 60.
  • Steam, heated gas or some other fluid (for clarity and brevity, hereinafter "steam") flows along the fluid path 40 and interacts with turbine buckets 70.
  • the steam is generally relatively hot at the forward turbine stage 50 and relatively cool at the aft turbine stage 60.
  • a spacer 80 is secured within the casing 20 and has an annular body 81, which may be tubular and/or substantially cylindrical and is formed with opposing outward and inward surfaces 82 and 83 that extend axially between forward and aft ends 84 and 85.
  • the annular body 81 is further formed with a tunability orifice (hereinafter "orifice") 90 extending through the body from the outward surface 82 to the inward surface 83.
  • the orifice 90 may be oriented in a substantially radial direction and may be plural in number. That is, the spacer 80 may have plural orifices 90 that are each circumferentially discrete and arrayed circumferentially around the rotor 30.
  • An assembly 100 secures the spacer 80 around the rotor 30 at an axial location between the forward turbine stage 50 and the aft turbine stage 60 such that the spacer 80 is positioned between sequential turbine buckets 110 and 111 with the orifice 90 opposing a turbine nozzle 112.
  • the spacer 80 forms an annular passage 120 around the rotor 30 which is defined between inward surface 83 and the surface of the rotor 30.
  • the steam flowing along the fluid path 40 toward the aft turbine stage 60 may at least partially flow into the annular passage 120.
  • the sequential turbine buckets 110 and 111 are among a plurality of like turbine buckets arrayed circumferentially around the rotor 30 at multiple turbine stages and are disposed to rotate about a longitudinal axis of the rotor 30 as the steam flows along the flow path 40.
  • the sequential turbine buckets 110 and 111 may each include a blade section 113, over which the steam flows, and a fir-tree section 114, which is insertable into a corresponding dovetail section of the rotor 30.
  • the assembly 100 may include mating flanges 101 and 102, which are disposed at the forward and aft sides of the spacer, and which are receivable in mating grooves 103 and 104 of aft and forward sides of the sequential turbine buckets 110 and 111.
  • the mating flanges 101 and 102 extend axially from the ends 84 and 85 of the spacer 80 and the mating grooves 103 and 104 are defined in opposing sides of the sequential turbine buckets 110 and 111. In some cases, the mating flanges 101 and 102 may extend from mid-sections of the opposing spacer ends 84 and 85.
  • a circuit 130 is fluidly coupled to the annular passage 120 and receptive of the steam that flows therein.
  • the circuit 130 is further configured to deliver the steam from an axial location between the forward turbine stage 50 and the aft turbine stage 60 to an axial location that is at least forward of the forward turbine stage 50 where it is employed for cooling.
  • the circuit 130 may be defined along various routes and through multiple features and generally skims along a surface of the rotor 30 while being insulated from the relatively hot steam flowing along the flow path 40.
  • An amount of the steam that flows into the annular passage 120 may be maintained within a predefined range. This range may be at least sufficient to ensure that enough steam is available to maintain operational conditions downstream from the aft turbine stage 60 and no more than necessary to provide a desired cooling effect at the forward turbine stage 50.
  • the circuit 130 may be defined through a gun hole 140 formed within at least the more forward sequential turbine bucket 110 and, in particular, within the fir-tree section 114 thereof.
  • the gun hole 140 may be oriented in a longitudinal direction that is generally in line with the rotor 130. Additional spacers at other turbine stages may be employed to insulate the cooled steam flowing along the circuit 130. These additional spacers form additional annular passages through which the circuit 130 may extend.
  • the gun hole 140 may be circumferentially discrete and provided as part of a plurality of gun holes 140 that are arrayed circumferentially about the rotor 30. Each of the plurality of gun holes 140 may be fluidly coupled to the annular passage 120 and the additional annular passages.
  • the circuit 130 may be configured to deliver the steam to, for example, a packing head region 150 or any region disposed forward of the forward turbine stage 50 that has a pressure that is lower than that of the axial location between the forward turbine stage 50 and the aft turbine stage 60 (i.e., an extraction region defined around the spacer 80).
  • the steam may be delivered to a surface of a turbine bucket.
  • the cooled steam may be employed to effectively reduce temperatures forward of the forward stage 50 such that more highly heated steam can be permitted to enter the flow path 40 without risking excessive damage.
  • the turbine 10 may further include a spacer plug 160, which may be employed to selectively close the orifice 90. In this way, the amount of steam permitted to enter the annular passage 120 can be increased, decreased, maximized or cut off completely.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11162097.7A 2010-04-14 2011-04-12 Entretoise de moteur de turbine Not-in-force EP2378070B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/759,811 US8376689B2 (en) 2010-04-14 2010-04-14 Turbine engine spacer

Publications (3)

Publication Number Publication Date
EP2378070A2 true EP2378070A2 (fr) 2011-10-19
EP2378070A3 EP2378070A3 (fr) 2014-09-24
EP2378070B1 EP2378070B1 (fr) 2018-07-18

Family

ID=44244833

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11162097.7A Not-in-force EP2378070B1 (fr) 2010-04-14 2011-04-12 Entretoise de moteur de turbine

Country Status (4)

Country Link
US (1) US8376689B2 (fr)
EP (1) EP2378070B1 (fr)
JP (1) JP5276689B2 (fr)
RU (1) RU2011113993A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3112694A1 (fr) * 2015-07-01 2017-01-04 Techspace Aero S.A. Tambour perfore de compresseur de turbomachine axiale

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8961132B2 (en) * 2011-10-28 2015-02-24 United Technologies Corporation Secondary flow arrangement for slotted rotor
US8992168B2 (en) * 2011-10-28 2015-03-31 United Technologies Corporation Rotating vane seal with cooling air passages
US9528376B2 (en) * 2012-09-13 2016-12-27 General Electric Company Compressor fairing segment
US9441639B2 (en) * 2013-05-13 2016-09-13 General Electric Company Compressor rotor heat shield
WO2015072089A1 (fr) 2013-11-15 2015-05-21 日本電気株式会社 Système et procédé de compensation d'écarts de fréquence
US10837288B2 (en) 2014-09-17 2020-11-17 Raytheon Technologies Corporation Secondary flowpath system for a gas turbine engine
DE102014224844A1 (de) 2014-12-04 2016-06-09 Siemens Aktiengesellschaft Rotor, Axialverdichter, Verfahren zur Montage

Family Cites Families (14)

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JPS52103204U (fr) * 1976-02-04 1977-08-05
JPS5361501U (fr) * 1976-10-26 1978-05-25
JPS57168005A (en) * 1981-04-10 1982-10-16 Hitachi Ltd Rotor structue for axial machines
JPS6093101A (ja) * 1983-10-28 1985-05-24 Hitachi Ltd 蒸気タ−ビンのロ−タの温度上昇防止装置
DE3606597C1 (de) * 1986-02-28 1987-02-19 Mtu Muenchen Gmbh Schaufel- und Dichtspaltoptimierungseinrichtung fuer Verdichter von Gasturbinentriebwerken
JP3780608B2 (ja) * 1997-03-19 2006-05-31 株式会社日立製作所 ガスタービン
JP3901828B2 (ja) * 1998-02-17 2007-04-04 三菱重工業株式会社 蒸気冷却ガスタービン
FR2825748B1 (fr) * 2001-06-07 2003-11-07 Snecma Moteurs Agencement de rotor de turbomachine a deux disques aubages separes par une entretoise
US6558118B1 (en) * 2001-11-01 2003-05-06 General Electric Company Bucket dovetail bridge member and method for eliminating thermal bowing of steam turbine rotors
EP1452688A1 (fr) 2003-02-05 2004-09-01 Siemens Aktiengesellschaft Rotor pour une turbine à vapeur, procédé et utilisation de refroidissement d'un tel rotor
US7017349B2 (en) * 2003-02-05 2006-03-28 Mitsubishi Heavy Industries, Ltd. Gas turbine and bleeding method thereof
US20070065273A1 (en) * 2005-09-22 2007-03-22 General Electric Company Methods and apparatus for double flow turbine first stage cooling
GB0603030D0 (en) * 2006-02-15 2006-03-29 Rolls Royce Plc Gas turbine engine rotor ventilation arrangement
US8348608B2 (en) * 2009-10-14 2013-01-08 General Electric Company Turbomachine rotor cooling

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3112694A1 (fr) * 2015-07-01 2017-01-04 Techspace Aero S.A. Tambour perfore de compresseur de turbomachine axiale
BE1023233B1 (fr) * 2015-07-01 2017-01-05 Safran Aero Boosters S.A. Tambour perfore de compresseur de turbomachine axiale
US10273977B2 (en) 2015-07-01 2019-04-30 Safran Aero Boosters Sa Perforated drum of a compressor of an axial turbine engine

Also Published As

Publication number Publication date
US20110255977A1 (en) 2011-10-20
US8376689B2 (en) 2013-02-19
JP5276689B2 (ja) 2013-08-28
EP2378070A3 (fr) 2014-09-24
RU2011113993A (ru) 2012-10-20
EP2378070B1 (fr) 2018-07-18
JP2011226478A (ja) 2011-11-10

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